Honeywell International Inc.

Allan Blunt

Casey Hanlon

James Neil Quitmeyer

Kellan P Geck

Russ Ether

Mark B Hanson

Jeffrey K Arnold

Allen R Gale

Leo H McWilliams

A system and method of controlling aircraft brakes in an aircraft that includes a brake pedal and an electric brake actuator. An aircraft operational state is determined and an application force that is supplied to the brake pedal is determined. When the determined aircraft operational state is a ground-idle state and the determined application force is greater than a set force magnitude, an actuator brake is moved to engage the electric brake actuator and the electric brake actuator is de-energized.

Aircraft electric brake actuation system and method

An aircraft brake system electromechanical actuator is provided. The actuator is configured with features that allow the electric motor to be a line replaceable unit. One such feature is a foreign-object-damage shield that inhibits dust, debris, and/or other particulate contaminants from entering the electromechanical actuator during electric motor removal and replacement.

Brake actuator assembly with line replaceable motor features

A combination brake and anti-lock system for a wheeled vehicle such as an aircraft includes an operator controlled source of pressurized hydraulic fluid for selectively applying hydraulic pressure to a hydraulically actuated wheel rotation braking device which responds to the applied hydraulic pressure to apply a braking force to a wheel of the vehicle to thereby arresting wheel motion. There is a low pressure hydraulic fluid return with a normally open hold valve in circuit between the source and the braking device for selectively opening and closing a fluid flow path from the source to the braking device and a normally closed decay valve in circuit between the braking device and the return for selectively opening and closing a fluid flow path from the braking device to the return. A wheel speed sensing device provides an indication of the rotational speed of the wheel and a valve control responds to an indication of a skid indicative wheel speed irregularity from the sensing device to close the normally open valve and open the normally closed valve. The valve control may be disabled manually by an operator on command or automatically upon detecting an anti-skid malfunction.

Anti-lock braking system module for aircraft equipped with master cylinder brake systems

A process of enhancing repeatability of the force applied to an object by an electromechanical system having an electric motor, a rotary to linear motion converter and a gear train mechanically coupling the motor to the converter includes providing an analog signal having a magnitude indicative of the desired force, supplying the analog signal to the motor to apply force to the object, removing the analog signal from the motor and reapplying the signal before any free play motion within the converter and gear train can occur. During a command for a desired force, the sequence of supplying the analog signal to the motor to apply force to the object, removing the analog signal from the motor, and resupplying the analog signal to the motor prior to any free play motion occurring within the gear train and converter are repeated several times. The rapid reapplication of the analog signal prevents any backlash associated with the gear train and converter. The process may be employed to selectively apply a compressive force to a compressible stack of interleaved braking disks to apply a braking force to a rotating wheel where an operator initiated digital braking command indicative of a desired braking force is converted to an analog signal having a magnitude indicative of the desired braking force to provide more consistent wheel braking in response to specific braking force commands.

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Granger, IN, United States of America

Allan Blunt